Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer, inner ceramic layer and outer ceramic layer.
1. A layer system adapted for use in a high temperature environment, comprising:
a substrate;
a metallic bond layer arranged on the substrate comprising:
24-26 wt % cobalt,
16-18 wt % chromium,
9.5-11 wt % aluminum,
0.3-0.5 wt % yttrium,
0.5-2 wt % rhenium, and
remainder nickel;
a yttrium-stabilized zirconium oxide inner ceramic layer arranged on the bond layer; and
an outer ceramic layer arranged on the inner ceramic layer comprising:
80 wt % of a Gd 2 Zr 2 O 7 pyrochlore.
2. The layer system as claimed in claim 1 , wherein the layer system consists essentially of: the substrate, the metallic bond layer, the inner ceramic layer and the outer ceramic layer.
3. The layer system as claimed in claim 1 , wherein the outer ceramic layer comprises 100 wt % of the Gd 2 Zr 2 O 7 pyrochlore.
4. The turbine blade or vane claimed in claim 1 , wherein the substrate has a single crystal structure.
5. A high temperature coated turbine component, comprising:
a substrate formed from a nickel-based or cobalt-based super alloy;
a metallic bond layer arranged on the substrate comprising:
11-13 wt % cobalt,
20-22 wt % chromium,
10.5-11.5 wt % aluminum,
0.3-0.5 wt % yttrium,
1.5-2.5 wt % rhenium, and
remainder nickel;
a yttrium-stabilized zirconium oxide inner ceramic layer arranged on the bond layer; and
an outer ceramic layer arranged on the inner ceramic layer comprising:
80 wt % of a Gd 2 Hf 2 O 7 pyrochlore.
6. The coated turbine component claimed in claim 5 , wherein the coated turbine component consists essentially of: the substrate, the metallic bond layer, the inner ceramic layer and the outer ceramic layer.
7. The coated turbine component claimed in claim 5 , wherein the outer ceramic layer comprises 100 wt % of the Gd 2 Hf 2 O 7 pyrochlore.
8. The turbine blade or vane claimed in claim 5 , wherein the high temperature coated turbine component is a blade or vane.
9. The coated turbine component claimed in claim 8 , wherein the superalloy substrate has a single crystal structure.
10. The coated turbine component claimed in claim 5 , wherein the yttrium-stabilized zirconium oxide inner ceramic layer is applied via a plasma-spray or an electron beam physical vapor deposition process.